Cowling arrangement



7 June 3, 1947.- H. w. ELKIN COWLING ARRANGEMENT Filed Oct. 9, 1944 3 Sheets-Sheet 1 m w m m HUGH W ELKJN AGENT June 3, 1947. H. w. ELKIN 2,421,689 I comma ARRANGEMENT Filed Oct. 9, 1944 3 Sheets-Sheet 2 IINVENTOR. HUGH WI .E'LKJN AGENT June 3, H w ELKN COWLQLNG ARRANGEMENT 5 Sheets-Sheet 5 Filed Oct. 9, 1944 INVENTOR. [52/551 WI EZK/N AGENT 5. g g s Patented June 3, 1947 UNITED STATES PATENT OFFICE Lockheed Aircraft Corporation,

Calif.

' Burbank,

Application October 9, 1944, Serial No. 557,752

8 Claims. 1

. accessibility tothe engine.

It has been the general practice to construct the cowls for aircraft engines in two or more removable panels or sections and to attach the panels to the supporting structures by means of multiplicities'of fastening devices. In order to inspect and service the engine it is necessary to frequently removethe panels, and for this reason, the fastening devices employed have been of the typesthat are readily releasable. Although the fasteners are usually of a quick release type, the operations necessary to release andthen reconneat the multitude of. fasteners each time a panel is removed and replaced are very tedious and time consuming. The large number of fasteners isalso undesirable from an aero-dynamic standpoint, producing substantial drag. Furthermore, the quick release fasteners heretofore employed on engine cowls have been relatively small and subject to breakageand distortion as a result of the repeated removal and reattachment of the panels, accompanying the essential servicing of "the engine.

An important object of the invention is to provide a cowl assembly for aircraft engines, and

the panels in the operative positions or to release the panels for free removal. A simple screw driver or similar tool serves to lock and release the securing means of i the invention.

. Another object of the invention is to provide an engine cowling assembly in which the cowl panels are completely removable as individual elements, thus permitting free access to the whole or part of theengine. Upon the release of the securing means, the panels are entirely detached andmay be removed from the airplane. to give full access to the engine.

Another object of the invention is to provide a cowl assembly for aircraft engines presenting an external surface havinga minimum of interruptions and irregularities, thereby reducing drag.

The securing or attaching means of the cowl sections embody relatively small levers which may a lie flush with the cowl surfaces, and with the exception of these levers, no other breaks, interruptions or irregularities are present in the surface.

It is another object of the invention to provide a cowling structure characterized by dependable cam means which assure the retention of the cowl sections in firm contact with the. supporting structure and which are adjustable to obtain the most efficient securing action. The cowl sections are formedwith grooves or channels for receiving ring elements of the supporting framework and the cam means operates to initially bring the channels into full pressure engagement with the ringelements and then releasably locks the panels in the positions where this engagement is maintained to preventpanel vibration.

A further object of the invention is to provide a combined supporting structure and cowl panel assembly in whichall fore and aft cowl loads are transmitted through the above referred to cam means to fore and aft beams, which in turn, transmit the loads to the airplane structure proper while all bursting air loads imposed on the cowl panels are transmitted directly from the panels to supporting rings of the framework, which rings carrysuch loads under tension. The construction is such that all fore and aft cowl loads are transmitted or applied directly to the framework of the nacelle without affecting the supporting rings and is such that the rings act under tension to independently assume all radial cowl loads.

A further object of the invention is to provide a cowl structure in which the cam action maintains substantially airtight contact between the cowl panels and the fixed airplane structure so I that the ducts in the panel sections are kept in Figure 1 is a perspective view of the assembled,

cowl panels;

Figure 2 is an-enlarged fragmentary perspective view showing the manner in which a cowl 3 panel cooperates with the rings of the supporting framework;

Figure 3 is a view similar to Figure 1 showing one panel in position for attachment to the supporting framework;

Figure 4 is a view similar to Figure 2 showing the cam lever in the released position and illustrating the panel in position for attachment to the framework;

Figure 5 is a perspective view of the cowl panel supporting framework with the panels removed and illustrating a portion of the nacelle frame;

Figure 6 is a perspective View of one of the cowl panels as detached from the assembly;

Figure 7 is an enlarged fragmentary sectional view taken substantially as indicated by line I? on Figure 9;

Figure 8 is an enlarged fragmentary detailed sectional view taken substantially as indicated by line 83 on Figure l Figure 9 is an enlarged fragmentary perspective view illustrating one of the cams in associa tion with its cam stops;

Figure 10 is an enlarged horizontal detailed sectional view of a cam stop and its adjustment stud, taken substantially as indicated by line Ill-Iil on Figure 11; and

Figure 11 is a front elevation of the cam stop and its adjustment means.

The cowling arrangement of the invention may be employed on aircraft of different characters and in association with various types of aircraft power plants, being capable of considerable variation to adapt it for given applications. In the drawings I have illustrated the invention embodied in a form suitable for use with a radial air-cooled engine, and I will proceed with a detailed description of the illustrated structure, it being understood that this is only one preferred embodiment and application.

Referring first to Figure 5, it will be seen that the supporting structure or framework of the cowling assembly comprises a forward ring IS, an aft ring I I and a plurality of circumferentially spaced fore and aft beams I2. The rings I!) and II may be of channel stock constructed to have the channels at their aft sides. The aft ring II is'somewhat larger in diameter than the forward ring I6 and is interrupted at circumferentially spaced points by blocks I3. The blocks I3 may be castings of selected metal or alloy, and the sections of the ring II are rigidly fixed to them so that the assembly forms a continuous ring-like unit; The fore and aft beam members IA of the nacelle, not shown, are secured to the blocks I3 by suitable terminal connections. It will be observed that the aft ring I i is made up of a plurality of sections secured between terminal blocks I 3 on the forward end of the nacelle framework.

The fore and aft beams I 2 of the cowling framework occur at the lines of division or joinder of the cowl panels and the number and disposition of the beams are governed by the number and location of the panels. In the particular construction illustrated, there are four panels, namely, two side panels I5, a top panel I5 and a bottom panel I I. The panels are of substantially equal circumferential extent, and there are four substantially equally spaced fore and aft beams I2. The forward ends of the beams I2 are suitably riveted, bolted, or otherwise fixed to the forward ring II! and the rear ends of the beams are secured to the terminal blocks I3 by terminal connections. The beam I2 may be of any selected or required cross sectional configuration. As best illustrated in Figures 8 and 9, the beams I2 are box-like elements having spaced side walls I8 that are generally radial with respect to the central longitudinal axis of the assembly. The outer walls of the beams I2 are channeled or grooved to carry chafing pads I9; see Figures 8 and 9. These pads I9 are omitted from Figure 5 to clarify the showing. The upper and lower sections of the aft ring I I are provided with air duct ports 28), and may carry similar chafing and sealing pads. Circumferentially spaced locating pins 2! project from the forward face of the aft ring II to assist in locating the cowl panels as will be later described. The cowl sections or panels I5, I6 and I! are independently separable elements normally assembled on the above described supporting framework to constitute a tubular cowling for the engine. The configuration of the panels will vary in different applications of the invention. In the case illustrated, the panels I5, I6 and I! are substantially alike in shape and are elongate elements each having a transverse or circumferential curvature of about The construction of the panels is subject to considerable variation. For the purpose of the present disclosure, it will be assumed that each panel I5, I6 and I! is comprised of an outer skin 22, a suitable internal stiffening and strengthening structure and an internal skin 24. The invention is not primarily concerned with the details of the internal panel elements, and these parts have been omitted from the drawings to clarify the showing. However, I have shown fore and aft stiflening and reinforcing elements 23 of the internal panel assemblies extending along the longitudinal edges of the panels. These elements 23 are stepped back from the edges of the panels and lie in spaced relation to the beams I2, when the panels are in position on the supporting structure. The inner skins 24 of the panels may cover the fore and aft stiffening elements 23. The forward ends of the panels I5, I6 and I! have contoured inner aprons 25 defining the throat or mouth of the cowl assembly. The upper and lower cowl panels I16 and Il are provided with fore and aft ducts 25 leading from the forward end of the assembly to the duct ports 20 of the aft supporting ring II. The longitudinal edges of the panels are preferably straight and related to come into abutment or parallel adjacent relation directly over the beams I2 as best shown in Figure 8.

i In accordance with the invention, the panels I5, I6 and I! are constructed to cooperate with the fore and aft rings I0 and II for the transmission of radial loads. The rear edge portions of each panel has a rearwardly facing groove or channel 21 for receiving the aft ring II; see Figures 2, 4 and 6. The forward portions of the panels I5, I6 and I1, adjacent the inner edges of the aprons 25, have similar channels 28 for receiving or cooperating with the forward supporting ring Ill. The channels 21 and 28 are circumferentially curved and are proportioned to accurately conform to the rings II] and II. The channels 27 and 28 may be constructed to have continuous engagement with the supporting rings throughout the transverse or circumferential extent of their respective panels I5, I6 and I 1. It is desirable to have the two channels 27 and 28 of a panel spaced and related so as to both have full cooperation with their respective supporting rings II and I 0. It will be apparent that upon correctly orienting a panel with. respect to the esupportingnstructuret a; simple; rearward Emotion 12,42 gees of the panel brings its grooves into simultaneous -.ooop.e'ration.with theforiecand aft ringsil land I l. tjThi-fil afill BhfiSFOfIIthE"panels ll 5,". I Etand: [I have :5[10li6t3' lonzopeningssfiitfor i-receivingcthe above l. :idescribedlooatonpins 2 LS1 "The cooperationlofthe I pins: 2 and; openings- 2e definitelyaslocates the ":l 2tiandzig tgr lw t ng y ith :panels initheiizcorrect circumferential: positions. "ates 1evei '34 upon pivoti-ng of 'the 1-; eWithv-the assemblywthus Ian-described; it:=:wil1 E -leven between ts raised} andlowered ds'itions. he seen-that the'panel's 155716 and. are depende -tzrhgzf i-wgmtst p ib i utm' gl 39; e n g g Wablywsupported;againstradialloadingtinbothwdiby the surfaces 42 and 43 of the cam leverto erections. ,iThe invention.vprovidesit dependable, reflect rearward movernent otthepane1 and thus e ilytoperatedl means for efiectively supportin bring its channels 21 and zs mte effective cooptthe panels aga-inst axial" orfore and; aft loading, "eration' with the supporting rings H and. The a-andafor movingthe panels axially between ;the m -abutment 39 is-in the-nature-of a projecting-lip epositions-twhere 1 they; are hooked; or 1 engaged" on or fiange on: a; bracket like' base": 46 Whichengages the supp rt ne-ri esfi a d Il and t etp sitions the walhlii of th beam- 12. In accordance-with where they aregfree otthe rings. These rmeans the' invention the cam mechanism embodies "an are inrthe fcrmof cam mechanisms and are charadjustment itmeans. In the "case illustrated the Q F ZBQ -lth mp 9 their construction r stop -or abu tmLnt SQ is adjustable axiaily' of the n the? 5 0 $11911 p ra o fl m mea beam'fli to assurecorrect operation Ofthe cam provided adiacent each long tud ed e o -mechanisnn-and to b'ring about firm engagement each pan ll e ll to c wi hs op of the channels and zs with; the'-supporting or abutments on the beams E2 of the s uppolting rings l'fl and IA Spaced openings 41' are'provided.

structure. I will proceed with adescription of a 5125 thelbasez(4B"ofitheja butmentttolreceiveattachsin l am mean 0 ;-.t p e f I it b ne mg bolts-'48. openings- '41Tare? elongated e r teeqthatt s i t n equa y app a longitudinally of the beam I 2-to allow axial eaf e e h ea fi e q l' s bfij n ie -justnient of the abutment relative to =thebo1ts48. fence numerals areapp ed te e r no dineln A'substantially central o ening 491s provid d in of 'thelsevera amdevices. the abutinent'base 46. The openin 49 receives V *3 v ,v a 'x ac am mlmcl e tflenrotatable metike edJusti g-stuetn. ec-

D3 Op ning 3| inthebraoket 3fi -calrics e will be Seen that upori ffrotation of thestud 50, t shaftw whlch wntmues wa d r u the sto es is adjusted fore or aftjdepending' upon a o t n v in 3 1 5 1? 7 a n fl tfi m the direction of" such""rotation. Means is prom t 1- he headf 9 t e-P M J?epeg vided for setting or securing the stud 50 in the i t the f r l v x the m adjustedmosition. A series of equally spaced fl mfl h e mi d f h G m lever notches 53is provided in the wall of the opening 1 '1 F S Q F i the P rfihef 3? 49 and. the exposed end of the stud 5n hast-two he f sfi i l v lQP i t e diametrically oppositefnotches 54; free Stud 50, h 1 and p i 9 ifgg 1 2 llwhen'turnedtb adjust theabutment' 39, is moved xtant;transits;attests: a eee e ete :headof the bolt-like shaft.- Thef prinejijm ge snotches 54 reg ster with a pair of diametrically L 9 i f 1s, tim pf ha l installed in ther'egistering notches 53 l and 54 to ed q lfgcmfcatemlever P secure the Stud inthe adjusted position. -=Fo1- i g tg me fsfi ifi i the P gt i I lowing adjustment er the abutment eab thestud 8 Dane 9' W 50 let the bolts as are tightened downto-seciirethe outward rotation of its arrrrBT. The opening 38 tmentimthe finalvposition the adjusiw is-shapedandqproportioned to accurately reoeive t t l d scribed f t 39 theleverand theouter-surfaoebf theleverarm i f g t the 2 g 3.1Lmaybe shaped to "conform to and lie flush with l a I thet'surfacebf theiskinZZ when the lever is'in 5 icam actlonlanddependable vlbra'tlon mslstmg opposite notches'53.' Pins or screws 55 arethen tits-flown or-actuated pbsitiony 'l'he outer skins 5 connectionofthelpainel itssupportmg Struc' :22 Off'llh' panelse'mayibelsmoothand unbroken r l l i l =except: for tthe' .openingsxttE and t the levers 34, The 5 Surface-4313 the leverlal flatly coop whichmormauy completely occupyuthempemngs erates withthe face of the abutment 39 when the andlliemflushziwithxtheaskinsurfaces tovreduce lever in its fully actuated position-"l This is dragtug, minimum l a l shown in Figure9of the drawings. ;In practice 34 is provided with Camiiaceg f it is preferred to have the cam lever 34 throw operatingwith spaced cam" stops or-abut tg 39 slightly past centerto bring its surface 43 into and 40 on the adjacent beam 12 of the supportfiat-Fngagement with abutment T inglframew'ork. As seeninFigureQ;the lever 34 tenslve engagement of the surface the has a rearwardly facing camsurface 4| for coopabutment 39 and the overcenter DOSltlOllOfthE eratingwith the abutnient ifl. ThesurfaceAI is fifi' t oe ade r tation of. the lever, curved adjacentits lowermend andwmergesl into and. the lever is automatically held "a a st disan upwardlyrand rforwardlyfiinclined .cam face-'41 placement from its fullyactuated position. Fur- :Thewfaceflitmay be.straight.and*flat, and. exthermore, the "extensivecooperation of, thesur- ;tends. upward1yandrlforwardly to -j i thi d facee43 withwthe abutmenta 39-provides for the surface-43:whichqissubstantially vertical ornordependableltlammission of forward axial'loads matte theloi'igitudinalaxis of the beamrlzwhen m th panel o the b 2 of the supthe lever:43:?is2iniits;operative position. t'Ihe exporting; structure. t; t t t posedilongitudinal edge'ofittheleverl 34ris out-back r .LThe stony-or tabutment 4llris i spaced aft ofsthe terial. l

. ;abutment 3 9 and isrigidly fixed to the beam l2 by rivets 56,-bolts or the like. The abutment 40 presents an active face which is in substantially parallel relation tothe abutment 39. The active face of the abutment 40 is engaged by the cam face 4| to cause forward movement of the panel [[5 for the purpose of releasing the channels 2'! v and 28 from the supporting rings II and H]. The flanges or active faces of the abutments 39 and 40 may be faced with pads 5'! of wear-resistant ma- The, invention may include means for positively locking'thecam levers 34 in the actuated positions with their'faces 43 in cooperation with the abutment 39 so as to lock the panels l5, l6, and

H inplace. Any appropriate means may be employed to lock the cam levers 34 in their down or actuated positions. In the drawings I have shown Dzus type studs 60 rotatably engaged in openings in theouter ends of the cam levers;

bayonet slots 6| into receiving relation to the spring 62 and is then rotated to move the bayonet slots into locking cooperation with the spring.

.A simple partial rotation of the stud 60 frees it from the spring 62, releasing the cam lever 34 for outward swinging. A simple tool T as illustrated in Figure-2 may be utilized to rotate the studs 60, and if required, may be employed in prying the levers 34 outwardly for ready manual engagement.

It is believed that the operation and features of the cowling arrangement will be apparent from the foregoing description. In applying a panel it is first necessary to bring the two levers 43 to the projecting position illustrated in Figures 4 and 6. With the levers in this position the panel is brought to aposition such as shown in the lower portion of Figure 3 where its openings 29 are aligned with the locator pins 2| and the cam portions of the levers 34 are then swung aft so that the cam surfaces 42 and 43 cooperate with the abutment 39 to force the panel aft.

The dam action moves the panel rearwardly to bring its channels 21 and 28 into tight engagement with the rings H and I0, When the levers 34 have been moved to their final flush positions in the openings--38 and the studs 60 are given a partial rotation, sothat their bayonet slots 6| interlock with the springs 62, the levers are positively locked in place. These operations are repeated in installing the several panels I5, l6 and I1.

Itshould be noted that the panels may be quickly installed and that there is no necessity for separately manipulating a multiplicity of individual fastening devices. With the panels installed,'all forward cowl loads are transmitted from the panels l5, l6 and I! to the beams 12 through the medium of the cam surfaces 43 and the abutments 39. This axial loading is transmitted from the beams 12 directly to the beam elements I4 of the nacelle, or air-frame. All radial loading on the cowl panels is transferred to the rings l I and H] by the channels 21 and 28, and this loading is distributed throughout the spaced rings. The rings and H act under tension in assuming the radial bursting-air loads imposed on the cowl panels and the loading of the rings is independent of the loadingof the beams l2. When it is desired to inspect or service the engine, the cowl panels may be removed individually and as many panels may be detached as is found necessary for the particular operation. In order to remove a cowl panel it is only necessary to partially rotate its studs 60 to release the slots 6| from the springs .62, whereupon the levers 34 are rotated forwardly. This forward rotation of the levers results in cooperation between the cam surfaces 4| and the aft abutment 40; The resultant cam action forces the cowl panel forwardly, releasing its channels 21 and 28 from the supporting rings II and It). With the channels released from the supporting rings, the panel is completely freed from the supporting structure.

Having described only a typical form of the invention, I do not wish to be limited to the specific details herein set forth, but wish toreserve to myself any variations or modifications. that may appear to those skilled in the art or fall within the scope of the following claims.

I claim:

1. An aircraft cowling assembly comprising a, supporting structure including an axially extending beam and a circumferentiall extending memher, a removable cowl panel having a channel for receiving said member for the transmission of radial loads between the panel and said structure, and means on the panel and said structure for shifting the panel axially to move the channel into and out of engagement with said member, said means including abutments on the beam and a rotatable cam on the panel for cooperating with the abutments.

2 An aircraft cowling assembly comprising a supporting structure including spaced axial beams and axially spaced circumferentially extending members, a cowl panel for arrangement on said structure and having axially spaced circumferentially extending grooves adapted to receive said members for the transmission of radial loads from the panel to said structure, and cam.elements on the panel and spaced beams for shifting the panel axially to move the channels into and out of engagement with said members and operable to transmit axial loads from the panel to said structure when the channels and said members are in cooperation.

3. An aircraft cowling assembly comprising a supporting structure including spaced axial beams and axially spaced circumferentially extending members, a cowl panel adapted to be removably engaged on the supporting structure, the panel having rearwardly facing channels adjacent its fore and aft ends adapted to receive said members for the transmission of radial loads between the panel and said structure, and releasable means for holding the panel in the position where its channels cooperate with said members and operable to transmit axial loads between the panel and said structure. r

4. An aircraft cowling assembly'comprising a supporting structure including spaced axially extending beams, and axially spaced circumferentially extending members connected with the beams, a, plurality of cowl panels adapted to be removably supported on said structure, each panel having axially spaced channels for receiving said members for the transference of radial loads between the panels andsaid structure, and means for shifting the individualpanels axially to bring their channels into receiving engagement with .9 said members and thereaftertransfer axial loads between the panels and said structure.

5. An aircraft cowling assembly comprising a supporting structure including spaced axially extending beams, and axially spaced circumferentially extending members connected with the beams, a plurality of cowl panels adapted to be removably supported on said structure, each panel having axially spaced channels for receiving said members for the transference of radial loads between the panels and said structure, and means for shifting the individual panels axially to bring their channels into receiving engagement with said members and thereafter transfer axial loads between the panels and said structure for the transference of radial loads between the panels and said structure, said means including cooperable cam elements on the panels and said beams.

6. A cowl assembly comprising a supporting structure, a cowl panel for arrangement on said structure, parts on said structure and panel at the fore and aft ends of the panel adapted to have interfitting engagement for the transference of loads between the panel and structure in one direction, and means for shifting the panel axially to bring said parts into interfitting engagement and for thereafter transferring loads between the panel and structure in the other direction including spaced abutments on said structure, and a cam on the panel for cooperating with the abutments.

7. A cowl assembly comprising a supporting structure, a cowl panel for arrangement on said structure, parts on said structure and panel adapted to have interfitting engagement for the transference of loads between the panel and structure in one direction, and means operable to shift the panel axially with respect to said structure to bring said parts into cooperation and for thereafter transferring loads between the panel and structure in the other direction, said means including spaced abutments on said structure, a cam on the panel for cooperating with the abutments, and means for adjusting at least one of the abutments.

8. An aircraft cowling assembly comprising a supporting structure including spaced axially extending beams, and axially spaced circumferentially extending members connected with the beams, a plurality of cowl panels adapted to be removably supported on said structure, each panel having axially spaced channels for receiving said members for the transference of radial loads between the panels and said structure, and means for shifting the individual panels axially to bring their channels into receiving engagement with said members, and thereafter transfer axial loads between the panels and said structure, said means including pairs of spaced abutments on the beams, a lever rotatably supported on each paneladjacent each axial edge of the same, and cam. parts on the levers for cooperating with said abutments.

HUGH W. ELKIN.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Name Date Chilton Feb. '7, 1933 Breene et al July 21, 1936 Lawry Nov. 7, 1944 OTHER REFERENCES Number 

